Refinement of Dynamic Finite Element Models from the Garteur AG14 Collaborative Programme

2007 ◽  
Author(s):  
Nick Lieven ◽  
Jon Coote ◽  
Mike Friswell ◽  
Colin Hatch ◽  
Graham Skingle ◽  
...  
Keyword(s):  
Finite Element ◽  
Finite Element Models ◽  
Dynamic Finite Element

Affordable structural optimization for large-size dynamic finite element models

1997 ◽  
Author(s):  
Francois Hemez ◽  
Emmanuel Pagnacco ◽  
Francois Hemez ◽  
Emmanuel Pagnacco
Keyword(s):  
Finite Element ◽  
Structural Optimization ◽  
Finite Element Models ◽  
Dynamic Finite Element ◽  
Large Size

Viscoelastic characterization of soft tissue from dynamic finite element models

2008 ◽  
Vol 53 (22) ◽  
pp. 6569-6590 ◽  
Author(s):  
Hani Eskandari ◽  
Septimiu E Salcudean ◽  
Robert Rohling ◽  
Jacques Ohayon
Keyword(s):  
Finite Element ◽  
Soft Tissue ◽  
Finite Element Models ◽  
Dynamic Finite Element

Toward the updating of large-scale dynamic finite element models using massive instrumentation

1996 ◽  
Author(s):  
Francois Hemez ◽  
Charbel Farhat ◽  
Emmanuele Decaux ◽  
Jacques Duysens ◽  
Pascal L
Keyword(s):  
Finite Element ◽  
Large Scale ◽  
Finite Element Models ◽  
Dynamic Finite Element

Experimental Correlation of Dynamic Finite Element Models

1995 ◽  
Author(s):  
Raymond E. Martin ◽  
David M. O’Brien
Keyword(s):  
Finite Element ◽  
Finite Element Models ◽  
Fe Model ◽  
Dynamic Finite Element ◽  
Aircraft Landing ◽  
Modal Model ◽  
Analytical Development ◽  
Structure Correlation ◽  
Operational Data ◽  
Wheel Brake

Abstract Finite element models used in the dynamic analysis of structures benefit from correlation with experimental data at each step in the analytical development. The steps Aircraft Landing Systems has followed in obtaining both modal and operational data for the validation of aircraft wheel, brake, and strut FEA models are discussed in this paper. These steps include the creation of a valid experimental modal model for major components in the structure, correlation of the modal results to tie FE model results, testing of sub-assemblies, and collecting data from dynamometer tests of the system and their correlation to the assembled FE model of the system. Various procedures are described which have been developed and adapted by Aircraft Landing Systems and which enable practical correlation to frequencies as high as 2000 Hz. The application of the procedures are demonstrated with examples from recent testing.

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